Implications of engine's deterioration upon an aero-engine HP turbine blade's thermal fatigue life

被引：24
作者：
Naeem, M [1 ]
Singh, R
Probert, D
机构：
[1] PAF Base Faisal, Cent Tech Dev Unit, Karachi, Pakistan
[2] Cranfield Univ, Sch Mech Engn, Cranfield MK43 0AL, Beds, England
来源：
INTERNATIONAL JOURNAL OF FATIGUE | 2000年 / 22卷 / 02期
关键词：
engine deterioration; equivalent full thermal cycle; thermal fatigue; turbine's entry temperature;
D O I：
10.1016/S0142-1123(99)00105-X
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
Possessing a better knowledge of the impacts of engine deterioration upon an aircraft's performance as well as its fuel and component life usage, helps the users make wiser management decisions and hence achieve improved engine utilization. For a military aircraft, using a computer performance simulation, the consequences of engine deterioration on a high pressure turbine blade's thermal fatigue life are predicted. (C) 2000 Elsevier Science Ltd. All rights reserved.
引用
收藏
页码：147 / 160
页数：14
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